Blade or guide vane with raised areas

Abstract

The invention relates to a blade or vane, particularly of a turbine stage of a gas turbine, in particular of an aircraft gas turbine, having a blade or vane root and a blade or vane element joined to the blade or vane root, wherein the blade or vane element has a pressure side and a suction side, and wherein the blade or vane root has at least one raised region on its radial outer side facing the blade or vane element. It is proposed according to the invention that the blade or vane has a first raised region on the pressure side and a second raised region on the suction side, wherein the highest point of the first raised region is disposed essentially directly adjacent to the pressure side, and the highest point of the second raised region is disposed essentially directly adjacent to the suction side.

What is claimed is: 
     
       1. A blade or vane of an aircraft gas turbine, comprising:
 a blade or vane root and a blade or vane element joined to the blade or vane root, wherein the blade or vane element has a pressure side and a suction side, and wherein the blade or vane root has at least one raised region on its radial outer side facing the blade or vane element, wherein 
 the blade or vane has a first raised region on the pressure side and a second raised region on the suction side, wherein a highest point of the first raised region is disposed directly adjacent to the pressure side, and a highest point of the second raised region is disposed directly adjacent to the suction side, and 
 the highest point of the first raised region and the highest point of the second raised region lie in a front or leading one-half of an axial distance in the direction of flow, wherein the axial distance is a projection of a chord, which joins a leading edge region and a trailing edge region of the blade or vane element. 
 
     
     
       2. The blade or vane according to  claim 1 , wherein the highest point of the second raised region lies in a front or leading first one-fourth of the axial distance. 
     
     
       3. The blade or vane according to  claim 1 , wherein the highest point of the first raised region lies in a second one-fourth of the axial distance. 
     
     
       4. The blade or vane according to  claim 1 , wherein the blade or vane is a rotating blade or a guide vane. 
     
     
       5. The blade or vane according to  claim 1 , wherein a plurality of rotating blades is disposed next to one another in the peripheral direction and configured and arranged in a rotor having a rotor disk. 
     
     
       6. The blade or vane according to  claim 5 , wherein the rotating blades are joined to the rotor disk in form-fitting manner by means of their rotating blade root. 
     
     
       7. The blade or vane according to  claim 5 , wherein the rotating blades and the rotor disk are integrally joined to one another. 
     
     
       8. The blade or vane according to  claim 5 , wherein at least one rotor is configured and arranged in an aircraft gas turbine.